Patent application number | Description | Published |
20100080685 | Method and Apparatus for Gas Turbine Engine Temperature Management - A cooling system for a turbine engine, as well as a methodology for controlling the cooling system, is described. A valve member is disposed between a cooling fluid passage and a wheel space of the turbine engine and operates to admit cooling fluid to the wheel space for cooling thereof. The valve assembly is responsive to a condition in the wheel space and varies the flow of additional cooling fluid to the wheel space based on that condition. | 04-01-2010 |
20130054213 | PROCESS FOR ADAPTIVE MODELING OF PERFORMANCE DEGRADATION - The present subject matter is directed to methods and systems for providing adaptive modeling of performance degradation in a system, particularly, a gas turbine system. A performance model is provided and operated as both a calibration model and a baseline model. Data produced during both operations is stored and differences there between is used in adaptive logic, which may correspond to a neural network, to predict performance degradation to control operation of a system baseline model. Data from operation of the system baseline model may also be stored and used with data from the calibration model and baseline model in the adaptive logic. | 02-28-2013 |
20130066615 | SYSTEM AND METHOD FOR SIMULATING GAS TURBINE OPERATION - A method for simulating a gas turbine is disclosed. The method may generally include sensing values of a plurality of first operating parameters of a gas turbine, applying the first operating parameters to a model of the gas turbine to generate a plurality of predicted operating parameters, determining difference values between the predicted operating parameters and a corresponding plurality of sensed second operating parameters of the gas turbine, applying an error correction system to the difference values to determine correction factors and adjusting the model of the gas turbine using the correction factors, wherein the predicted operating parameters include at least one predicted combustion product parameter and the sensed second operating parameters include at least one sensed combustion product parameter. | 03-14-2013 |
20130174564 | SYSTEM AND METHOD FOR OPERATING A GAS TURBINE - A method for determining a cooling flow parameter of a cooling medium supplied through a gas turbine is disclosed. The method may generally include receiving a signal associated with a first value of a combustion product parameter at a location within a combustion zone of the gas turbine, receiving a signal associated with a second value of a combustion product parameter at a location downstream of the combustion zone, comparing the first and second values of the combustion product parameter and determining a cooling flow parameter of the cooling medium based on the comparison of the first and second values. | 07-11-2013 |
20130276458 | GAS TURBINE INLET SYSTEM AND METHOD - A gas turbomachine inlet system includes a duct member having an inlet portion fluidically coupled to an outlet portion through an intermediate portion. The inlet portion, outlet portion, and intermediate portion define a fluid flow zone. A throttling system is arranged in the duct member at one of the inlet portion, outlet portion and intermediate portion. The throttling system is configured and disposed to selectively establish a pressure drop through the fluid flow zone. A method of controlling inlet pressure drop through an inlet system for a gas turbomachine is also described herein. | 10-24-2013 |
20130305740 | METHOD AND APPARATUS FOR GAS TURBINE ENGINE TEMPERATURE MANAGEMENT - A turbine engine includes a turbine, a compressor for compressing air and a combustor for receiving the compressed air through an inlet passage and operable to burn fuel therewith to deliver hot exhaust gas to the turbine. Also included is a wheel space defined proximate to the combustor. Further included is a cooling air passage extending between the compressor and the wheel space. Yet further included is a valve assembly having a valve member disposed in the cooling air passage and operable to admit a cooling air to the wheel space in response to a condition therein. | 11-21-2013 |
20140182298 | STOICHIOMETRIC COMBUSTION CONTROL FOR GAS TURBINE SYSTEM WITH EXHAUST GAS RECIRCULATION - In one embodiment, a system includes at least one sensor configured to communicate a signal representative of a gas turbine operations. The system further includes a controller communicatively coupled to the sensor. The system additionally includes a stoichiometric model configured to receive one or more inputs representative of the gas turbine operations and a measured equivalence ratio, wherein the controller is configured to transform the signal into the one or more inputs and to use the stoichiometric model to derive an actuation signal based on a target equivalence ratio. | 07-03-2014 |
20140208755 | Gas Turbine Air Mass Flow Measuring System and Methods for Measuring Air Mass Flow in a Gas Turbine Inlet Duct - A method and system for measuring a mass flow rate in a portion of a flow path in an inlet duct of a gas turbine engine is provided. The system includes a sensor assembly attached to the inlet duct. The sensor assembly includes a tube with a longitudinal axis disposed in a substantially laminar flow region of the inlet duct, and a flow conditioner disposed in the tube. A hot wire sensor disposed in the tube is also provided. | 07-31-2014 |
20140260312 | SYSTEMS AND METHODS FOR GAS TURBINE TUNING AND CONTROL - A method of tuning a gas turbine includes receiving a first plurality of operating parameters as the gas turbine engine is operated at a first operating state. Further, the method includes operating the gas turbine engine at a second operating state to measure a second plurality of operating parameters at the second operating state. In addition, the method includes operating the gas turbine engine at a third operating state to measure a third plurality of operating parameters at the third operating state, wherein the first, second, and third operating states are different from each other. Additionally, the method includes generating a correction factor based on the first, second, and third plurality of operating parameters. The method also includes adjusting the operation of the gas turbine engine based on the correction factor. | 09-18-2014 |
20150081121 | SYSTEM AND METHOD FOR CONTROLLING OPERATION OF A GAS TURBINE BASED POWER PLANT - A system for controlling a gas turbine power plant includes a plurality of sensors configured to transmit signals indicative of one or more operating parameters of the gas turbine, and a control system in electronic communication with each sensor. The control system is configured to compute cumulative wear for one or more hardware components of the gas turbine based at least in part on the signals. Instructions are inputted into the control system which indicates a desired operational mode for the gas turbine. The control system may then compute a hardware consumption rate based at least in part on the cumulative wear. The hardware consumption rate may then be displayed to an operator via a display device. The operator may use the hardware consumption rate to determine potential economic impact of operating the gas turbine at the desired operational mode. | 03-19-2015 |